DE102014010109A1 - missile - Google Patents

Abstract

The invention relates to a missile (1) comprising a longitudinal axis (100) and comprising a base body (8), wherein the base body (8) extends along the longitudinal axis (100), a drive unit (7) which is electrically operable, and an energy store (4), with which electrical energy can be stored, wherein the energy store (4) within the base body (8) along the longitudinal axis (100) is arranged displaceably.

Description

The present invention relates to a missile, in particular an electrically driven missile.

Such a missile is for example from the DE10 2007 012 799 B3 known. This document discloses a missile with electric propeller modules, which are used for the propulsion and control of the missile. The power supply is ensured by a built-in accumulator.

One area of use of a missile, for example, is to guide an agent under high safety requirements and with high speed and high accuracy of hit into a moving target. Different requirements for the stability measure of a missile can be made in different flight phases. This static measure of stability of a missile is described by the following formula:

The dimensions of an exemplary missile 1 are in 4 shown. The stability measure Sn is determined by the distance from the pressure point Cp to the center of gravity Cg divided by the missile diameter D _ref . The measures x _Cg and x _Cp are the distances from the pressure point Cp and the center of gravity Cg to a reference point S0. During flight, the pressure point is changed locally, which depends on unimpairable different physical quantities. These are, for example, the angle of attack, the Mach number, the height or other sizes. The migration of the pressure point on the missile's longitudinal axis is indirectly constructed and uniquely determined by the design and the aerodynamic surfaces. Another important size in missile design is maneuverability. Maneuverability is a measure of the load multiple that a missile can produce in lift relative to its own weight. The stability measure and maneuverability are strongly related. This means that an increase in the stability measure results in a reduction in maneuverability and vice versa.

It is therefore a disadvantage of known missiles that stability measurement and maneuverability must already be determined during the design of the missile. A subsequent change is structurally possible only to a very limited extent.

In addition, in conventional missiles, the generated thrust is determined by the drive. In general, a generated engine thrust can not be changed. This means that the thrust from the ignition of the engine until its shutdown is consistently almost constant. Thus, even here, changes, especially during the flight, are not possible, so that the flexibility in the operation of the missile is very limited.

Finally, the range of conventional missiles depends to a large extent on the size of the engine used, i. H. of the caliber, the size itself and the weight of the engine. As a result, in the case of range increases, fundamental changes and thus cost-intensive new developments in terms of structure, aerodynamics, center of gravity and other aspects of the missile are often necessary.

It is therefore an object of the invention to provide a missile that allows for a simple and cost-effective production and assembly safe, reliable and flexible operation.

The object is achieved by the features of claim 1. Thus, the object is achieved by a missile comprising a main body, a drive unit and an energy storage. It is provided that the missile has a longitudinal axis, wherein the base body extends along the longitudinal axis. The drive unit is electrically operable and can be supplied with electrical energy from the energy store. According to the invention, it is provided that the energy store is arranged displaceably within the main body along the longitudinal axis. In this way, the focus of the missile is variable.

This is especially possible when the missile is in flight.

In previous missiles, the location of the center of gravity is subject to design requirements. One requirement is z. As in armor-piercing systems of action that the agent should be as far as possible on the nose of the missile. Due to the high ratio of small missiles between the mass of the active mass and the mass of the engine to the total mass, the active system and the drive system are therefore a decisive design driver for further construction. Other undesirable shifts in focus arise during flight in conventionally powered missiles by combustion of the fuel. Thus, the stability measure, and thus the agility of a conventional missile, already determined by the design of the missile and can not be actively changed later. Because of the described shifts in focus due to fuel consumption, the stability measure is always an unfavorable compromise. Here the allowed Invention by a corresponding positioning and / or moving the energy storage to set the focus of the missile and / or to vary. The energy storage is advantageously an accumulator, so that the weight of the missile does not change with increasing flight time. Thus, an accurate and flexible adjustment of the center of gravity is possible.

The dependent claims have advantageous developments of the invention to the content.

Preferably, the energy storage is displaceable by a displacement unit. It is provided in particular that the energy storage during the flight of the missile of the displacement unit is displaceable. Alternatively, it is preferably provided that the energy storage device is displaceable by the displacement unit before the flight in order to subsequently lock the energy store, so that the energy store is fixed during the flight.

In a particularly preferred embodiment of the invention, the displacement unit comprises a rail system. The rail system is advantageously oriented along the longitudinal axis, wherein the energy storage is displaceable and lockable on the rail system.

In a further particularly advantageous embodiment, the displacement unit has a spindle that can be driven by an electric motor. The energy store is preferably connected to the spindle in such a way that a rotation of the spindle causes a displacement of the energy store. In this way, the energy storage is displaceable during a flight of the missile, in which the electric motor drives the spindle. Particularly advantageous is also provided that the spindle has a self-locking, so that an independent movement of the energy storage is prevented.

The missile advantageously has at least two wings. Alternatively or additionally, the missile has aerodynamic control surfaces. It is provided that the aerodynamic control surfaces and / or the wings are arranged on the base body. If only two wings are provided, the missile is advantageously guided via a "bank to turn" steering mode in the target. If more than two wings are provided, the missile is advantageously guided into the target via a "skid to turn" mode. As an alternative to the aerodynamic control surfaces is also provided that thrusters are arranged on the base body. Particularly advantageous thrusters and aerodynamic control surfaces are used simultaneously.

In a particularly advantageous embodiment, the wings and / or the control surfaces are folded into the body. This allows in particular the launching of the missile from a container or from a directional launch tube. Thus, a handling of the missile is very flexible.

Advantageously, the missile is made of metallic components and / or fiber composite material and / or expanded polypropylene and / or other plastic materials.

In addition, to enable navigation and / or target detection, a seeker head is advantageously provided. The seeker head is arranged in particular at one end of the main body, wherein the seeker head is covered by a radome. The radome preferably has an aerodynamically favorable shape in order to reduce the aerodynamic drag of the missile. In particular, the seeker head comprises a gimbal platform system with which targets can be sighted independently of the direction of flight of the missile.

The drive unit of the missile is in particular an electric drive unit. The drive unit is also preferably designed such that it comprises a propeller module and / or impeller module. The required electrical energy for operating the propeller module and / or the impeller module can be removed from the energy store. Due to the electrical configuration of the drive unit of the thrust of the missile is advantageously variable.

Finally, it is particularly preferred that the missile has an active unit. A target can be combated with the active unit, and this can be done with non-lethal agents and / or with lethal agents. In this case, it is particularly advantageous that active units with different masses can be used, without the center of gravity of the missile being changed, since a shift in center of gravity can be compensated for by the different masses of the different active units by corresponding displacement of the energy accumulator along the longitudinal axis.

The invention will now be described in detail by means of embodiments with reference to the accompanying drawings. In the drawings is

1 a schematic representation of a missile according to a first embodiment of the invention,

2 a schematic representation of a missile according to a second embodiment of the invention,

3 a schematic representation of a missile according to a third embodiment of the invention, and

4 a schematic representation of a missile according to the prior art.

1 shows a schematic representation of a missile 1 according to a first embodiment of the invention. The missile 1 includes a main body 8th which has a cylindrical structure. The main body 8th thus extends along a longitudinal axis 100 , at the same time the longitudinal axis of the missile 1 forms. Furthermore, the missile includes 1 wings 2 and aerodynamic control surfaces 3 , By a drive unit 7 is the missile 1 drivable. The drive unit 7 is electrically configured, wherein electrical energy for operating the drive unit 7 in an energy store 4 is stored. The energy storage 4 is in particular an accumulator.

In addition, the missile points 1 an electric motor 6 on, a spindle 5 drives. The spindle 5 is with the energy storage 4 connected, with a rotation of the spindle 5 a shift of the energy store 4 along the longitudinal axis 100 causes. Thus, the focus of the missile 1 variable by the energy storage 4 is moved. As an alternative to the spindle 5 and the electric motor 6 is also possible to provide only a rail system with manual locking.

In the in 1 shown first embodiment, a total of four wings 2 provided, with the four wings 2 serve to generate lift. Thus, the missile becomes 1 guided to the finish via a "skid to turn" mode. Should only have two wings 2 be provided, so a "bank to turn" steering mode is used. The steering of the missile 1 takes place through the aerodynamic control surfaces 3 wherein, alternatively or in addition to the aerodynamic control surfaces 3 Thruster can be provided.

In the 1 illustrated wings 2 and control surfaces 3 are indicated only schematically. The real geometry and layout must be for the specific missile 1 be determined on the basis of dynamic and mechanical, structural and constructive aspects.

The front part of the missile 1 is the front-end module. The nose of the missile 1 has a radome 10 on which the aerodynamic drag of the missile 1 reduced and in the direction of the longitudinal axis 100 Behind arranged sensor components and control devices provides protection against environmental influences.

Behind the radome 10 is preferably a seeker 9 arranged, which decoupled from the position of the missile 1 , in particular with the aid of a gimbal platform system, can target a target. Alternatively, a gimbal platform system is not needed if the field of view of the seeker 9 for the specific use of the missile 1 is big enough. The seeker 9 For example, it is possible to work in the infrared range or in the visible range, wherein it is also possible for a radar device or another non-imaging search device, such as a semi-active laser detector, to be provided instead of the imaging seeker head. The information of the seeker 9 are relayed to the gimbal platform system or other direction finding system whose purpose is to identify the target, to track it and to provide processed data for a flight guidance system.

The missile 1 also has a data link, with the data and commands from an operator station to the missile 1 and telemetry data from the missile 1 are transferable to the operator station. In addition, a video transmission transmitter is provided, which makes it possible for the seeker head 9 to transfer images generated to the operator station or to another ground station. This allows a user, both before launching the missile 1 as well as after the start with the help of the seeker head 9 , the gimbal platform system and the data link to change the viewing direction up to 90 °, so as to perform an instruction process, that is to identify a target and mark. In particular, the user is a shooter who is using the missile 1 to act on a goal. The missile 1 is therefore advantageously man-in-the-loop through the data link.

As the drive unit 7 is electrically formed, is a major advantage of the missile 1 that one from the drive unit 7 generated drive thrust is variable. Should a user, as described above, have to carry out an instruction procedure for a destination, this can be achieved by reducing the drive thrust of the drive unit 7 a time for the briefing process to be increased so that the user has more time available. Once the briefing process is completed, the thrust can be increased again.

In addition, the missile points 1 an inertial measurement unit (not shown in detail in the following), which has three orthogonal rotation rate sensors and three orthogonal accelerometers and three magnetometers. The IMU can rely on the technology Electromechanical systems are based and has the task of providing information to a subordinate position control loop for stabilization and providing an inertial reference to the bearing angle supplied from a bearing to the target.

About a likewise not shown in detail satellite-based location system with antenna position can be done to the missile 1 to hold on a previously calculated trajectory. This is the missile 1 feasible in a predefined goal. Once the user reaches the destination through the seeker head 9 he can identify and mark the target. Then the target approach of the missile begins 1 while the missile 1 the further target tracking autonomously takes over, until it comes to the final collision.

In addition, the missile points 1 an unillustrated pitot tube, which serves the measurement of the flow velocity and the determination of the adaptive loop gain for the above-mentioned flight guidance system.

The data of all sensory devices and information from the bidirectional data link are processed in the flight guidance system. The flight guidance system controls the thrust command, the position of the energy store 4 and the actuators of the controller for moving the aerodynamic control surfaces 3 , In addition to the aerodynamic control surfaces 3 it is also possible that a thrust vector control system is provided. This will be explained below 3 described.

The control commands provided by the flight guidance system serve both to control the actuators for actuating the control surfaces 3 or the thrust surfaces of jet thrusters, as well as the active displacement of the energy storage 4 through the spindle 5 and the electric motor 6 ,

Finally, it is envisaged that the missile 1 an active unit 11 includes. The active unit 11 may include non-lethal agents, such as tear gas, anesthetic gas, smoke grenades or stun grenades, as well as lethal agents, in particular explosives. By shifting the energy storage 4 within the body 8th are different acting entities 11 usable with different masses, without the focus of the missile 1 is changed.

The missile 1 points as in 1 illustrated, in the first embodiment, a drive unit 7 on, which includes four propeller modules. The propeller modules are between the wings 3 on an outside of the body 8th appropriate.

Another embodiment is in 2 shown. 2 schematically shows a second embodiment of the missile according to the invention 1 , wherein like reference numerals designate the same or similar components. Here is the basic structure of the missile 1 according to the second embodiment, almost identical to that of the first embodiment. A difference exists only in the drive unit 7 , This is how the missile points 1 according to the second embodiment as a drive unit 7 a propeller at the tail of the missile 1 on, with the propeller from an engine 12 is driven. The motor 12 is located inside the body 8th and is connected via a shaft in a Gasleitrohr with the propeller.

3 finally shows a third embodiment of the missile according to the invention 1 Also, the third embodiment is merely another drive unit 7 has, as the first or the second embodiment. Like reference numerals indicate the same or similar components.

In the third embodiment, the drive unit 7 an impeller module 13 on that inside the main body 8th is arranged. The impeller module 13 sucks air through an air intake 14 and gives this air through a nozzle 15 in the tail of the missile 1 out. Advantageously, the nozzle 15 equipped with a thrust vector control. These are nozzle servos 16 present, with which an alignment of the nozzle 15 relative to the longitudinal axis 100 is changeable. Alternatively, jet thrusters are in an outlet stream of the nozzle 15 present, so that the jet of the nozzle 15 is controllable.

As an alternative to the control described above, it is also possible in all embodiments, the missile 1 to control with a duck control. However, this is not shown in the figures for clarity. Duck control has aerodynamic control surfaces 3 seen in the direction of flight in front of the wings 2 ,

As a further alternative, it is also possible that the drive unit 7 on the wings 2 is arranged. By a rotation of the wings 2 opposite the main body 8th is thus a thrust vector control feasible. Alternatively, the drive unit 7 also at the control surfaces 3 be arranged.

It can thus be seen that the missile according to the invention 1 is very flexible to handle. It is by adjusting the center of gravity possible that the missile 1 for a variety of different activity units 11 and thus usable for various purposes.

LIST OF REFERENCE NUMBERS

1

missile

2

wings

3

control surfaces

4

energy storage

5

spindle

6

electric motor

7

drive unit

8th

body

9

seeker

10

Radom

11

effective unit

12

engine

13

Impellermodul

14

air intake

15

jet

16

nozzles servo

QUOTES INCLUDE IN THE DESCRIPTION

This list of the documents listed by the applicant has been generated automatically and is included solely for the better information of the reader. The list is not part of the German patent or utility model application. The DPMA assumes no liability for any errors or omissions.

Cited patent literature

• DE 102007012799 B3 [0002]

Claims (10)

Missile ( 1 ), having a longitudinal axis ( 100 ) and comprising - a basic body ( 8th ), whereby the main body ( 8th ) along the longitudinal axis ( 100 ), - a drive unit ( 7 ), which is electrically operable, and - an energy store ( 4 ), with the electrical energy can be stored, wherein the energy storage ( 4 ) within the body ( 8th ) along the longitudinal axis ( 100 ) is arranged displaceably. Missile ( 1 ) according to claim 1, characterized in that the energy store ( 4 ) is displaceable by a displacement unit. Missile ( 1 ) according to claim 2, characterized in that the displacement unit comprises a rail system which along the longitudinal axis ( 100 ) and on which the energy store ( 4 ) is displaceable and lockable. Missile ( 1 ) according to claim 2 or 3, characterized in that the displacement unit comprises a spindle ( 5 ), by an electric motor ( 6 ) is drivable, wherein the energy storage ( 4 ) in such a way with the spindle ( 5 ), that a rotation of the spindle ( 5 ) a shift of the energy store ( 4 ) causes. Missile ( 1 ) according to one of the preceding claims, characterized by at least two wings ( 2 ) and / or aerodynamic control surfaces ( 3 ), the wings ( 2 ) and / or the aerodynamic control surfaces ( 3 ) on the base body ( 8th ) are arranged. Missile ( 1 ) according to claim (5), characterized in that the wings ( 2 ) and / or the control surfaces ( 3 ) in the basic body ( 8th ) are foldable. Missile ( 1 ) according to one of the preceding claims, characterized in that the missile ( 1 ) is made of metallic components and / or made of fiber composite material and / or expanded polypropylene and / or other plastic materials. Missile ( 1 ) according to one of the preceding claims, characterized by a seeker head ( 9 ) at one end of the body ( 8th ), the seeker head ( 9 ) of a radome ( 10 ) is covered. Missile ( 1 ) according to one of the preceding claims, characterized in that the drive unit ( 7 ) at least one propeller module and / or an impeller module ( 13 ). Missile ( 1 ) according to one of the preceding claims, characterized by an active unit ( 11 ), with which a goal can be fought.

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